FIELD: control of spacecraft angular motion.
SUBSTANCE: proposed method includes measurement of total moment of momentum G in power gyroscope system and prediction of present magnitudes for performing each dynamic mode of spacecraft. At prediction, condition of belonging of vector G to definite fields of its magnitude for selecting required fields and composition of power gyroscope is checked. Many configurations of location of main and redundant power gyroscopes are fixed relative to axes of body basis. Fields of magnitudes of G are determined for each configuration. Configurations of power gyroscopes depend on spacecraft structural peculiarities and its dynamic modes. In the course of control of power gyroscope system, rational redistribution of service life of working power gyroscopes takes place at saving of service life of other systems of spacecraft. Proposed method provides for increase of fields of G magnitudes, thus making it possible to control this vector without switching-on power gyroscope jet engines.
EFFECT: enhanced controllability of spacecraft; minimization of consumption of propulsive mass of relief jet engines.
6 dwg
